CN117141744B - Dual-wheel landing gear course speed simulation test device in full-aircraft drop test - Google Patents
Dual-wheel landing gear course speed simulation test device in full-aircraft drop test Download PDFInfo
- Publication number
- CN117141744B CN117141744B CN202311429100.1A CN202311429100A CN117141744B CN 117141744 B CN117141744 B CN 117141744B CN 202311429100 A CN202311429100 A CN 202311429100A CN 117141744 B CN117141744 B CN 117141744B
- Authority
- CN
- China
- Prior art keywords
- landing gear
- disc
- gear wheel
- belt
- transmission
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 48
- 238000004088 simulation Methods 0.000 title claims abstract description 23
- 230000005540 biological transmission Effects 0.000 claims description 52
- 238000000034 method Methods 0.000 claims description 16
- 230000000712 assembly Effects 0.000 claims description 13
- 238000000429 assembly Methods 0.000 claims description 13
- 208000032369 Primary transmission Diseases 0.000 claims description 11
- 208000032370 Secondary transmission Diseases 0.000 claims description 11
- 230000000670 limiting effect Effects 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 3
- 230000002829 reductive effect Effects 0.000 description 3
- 230000001960 triggered effect Effects 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000005693 optoelectronics Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a double-wheel undercarriage course speed simulation test device in a full-aircraft drop test, which comprises a belt rotating device, an undercarriage wheel and two groups of photoelectric switches, wherein the belt rotating device is arranged on an aircraft main body and is connected with the undercarriage wheel; the landing gear wheels include nose landing gear wheels and main landing gear wheels; according to the invention, the first belt rotating device and the second belt rotating device are arranged, so that the rotation of the nose landing gear wheel and the main landing gear wheel is realized in the air, the full-aircraft shake-down course speed simulation test is performed, the action of external force is avoided, and the data precision and accuracy of the course speed simulation test are improved.
Description
Technical Field
The invention relates to the technical field of aircraft simulation test devices, in particular to a double-wheel landing gear course speed simulation test device in a full-aircraft drop test.
Background
The carrier-based aircraft is verified through a full-aircraft drop test because the ground load is large when landing, the aircraft has a course speed relative to the ground when landing, and real speed simulation cannot be performed in a test environment.
When the aircraft is tested, after the aircraft is lifted to the target height and the aircraft wheel is driven to rotate to the required rotating speed, the motor is manually controlled to stop after receiving the aircraft falling instruction, the stopping time deviation is large, the aircraft still has a period of time when falling to the ground, and the rotating speed of the aircraft wheel is attenuated to influence the test; patent CN208828090U discloses an all-electric servo-controlled landing gear wheel steering device for simulating the course speed simulation test of an aircraft, but the device cannot be applied to the all-aircraft landing test, and since the aircraft is lifted to be in a free state when the all-aircraft landing test is carried out, the aircraft cannot be kept stable when being subjected to external force, and therefore, the course speed simulation device placed on the ground cannot be adopted to prevent the aircraft from being influenced by the external force of the device.
Therefore, a dual-wheel landing gear course speed simulation test device in the full-machine drop test needs to be designed.
Disclosure of Invention
In order to solve the technical problems, the invention provides a double-wheel landing gear course speed simulation test device in a full-machine drop test.
The technical scheme of the invention is as follows: the double-wheel landing gear course speed simulation test device in the full-aircraft drop test comprises a belt rotating assembly, a landing gear wheel and two groups of photoelectric switches, wherein the belt rotating assembly is arranged on an aircraft main body and is connected with the landing gear wheel; the two groups of photoelectric switches are respectively arranged on the ground on the left side and the right side of the aircraft and are connected into a belt rotation control system;
the landing gear wheels comprise a nose landing gear wheel and two sets of main landing gear wheels;
the belt rotating assembly comprises a first belt rotating device connected with the nose landing gear wheels and two second belt rotating devices connected with the main landing gear wheels in a one-to-one correspondence manner;
the first belt rotating device comprises a first mounting seat, a transmission assembly arranged on the first mounting seat, a servo motor for providing power for the transmission assembly, and two groups of belt pulley assemblies connected with the transmission assembly, wherein the two groups of belt pulley assemblies are detachably connected with two sides of a nose landing gear wheel in a one-to-one correspondence manner respectively;
the second belt rotating device comprises a second mounting seat, a second driving disc arranged on the second mounting seat, a servo motor for providing power for the second driving disc, and a second driven disc connected with the second driving disc through belt transmission, wherein the second driven disc is detachably connected with the main landing gear wheel.
Description: according to the invention, the first belt rotating device and the second belt rotating device are arranged, so that the rotation of the front landing gear wheel and the main landing gear wheel is realized in the air, the course speed simulation test of the whole machine shaking down is performed, the action of external force is avoided, the accuracy of the test is improved, the first belt rotating device is recombined and designed to be also used for belt rotation of the main landing gear wheel, and the belt rotation can be automatically triggered to stop according to the falling of a falling system through the arranged photoelectric switch, so that the automatic stop of the belt rotation is realized, and the data precision and accuracy of the course speed simulation test are improved.
The photoelectric switch is a pair of transmitting and receiving light source devices, the transmitting light source is used for transmitting when the power is on, when the aircraft moves to the middle of the photoelectric switch, the receiving device is blocked from receiving the transmitted light source, signals are transmitted to the course speed simulation system, the speed simulation test device stops belt rotation, compared with the traditional manual closing mode, the time deviation can be effectively reduced, and the rotating speed of the landing gear wheel is not influenced by human factors.
Further, the transmission assembly comprises a transmission shaft, a primary transmission disc and a first driving disc, the transmission shaft is rotationally connected with a supporting block arranged at the bottom of the first installation seat, the primary transmission disc is fixedly sleeved on the transmission shaft, the first driving disc is connected with an output shaft of the servo motor, the first driving disc is in belt transmission connection with the primary transmission disc through a belt,
the belt pulley assembly comprises a secondary driving disc and a first driven disc, the secondary driving disc is in belt transmission connection with the first driven disc through a belt, the first driven disc is detachably connected with the nose landing gear wheel, and the secondary driving discs of the two groups of belt pulley assemblies are respectively arranged at two ends of the transmission shaft.
Description: the invention realizes the same-rotation-speed movement of the nose landing gear wheels through the transmission device, the belt pulley assembly and other parts, converts single driving of the servo motor into double driving, can reduce the requirement of driving equipment, improves the utilization rate of the driving equipment, realizes double-wheel belt rotation of one servo motor, can ensure the rotation speed of the two wheels to be consistent, and improves the test control precision.
Further, the rotational speed of the landing gear wheel is calculated using the following formula (1)N：
（1）
In the method, in the process of the invention,Vthe unit is m/s for the horizontal speed of the aircraft landing;Dis the diameter of the landing gear wheel, in m.
Description: the rotating speed of the landing gear wheel is determined through the landing gear horizontal speed and the diameter of the landing gear wheel, and the landing gear wheel is lifted to a specified speed through a servo motor to carry out a course speed simulation test.
Further, the rotation speed of a servo motor driving the nose landing gear wheels is calculated by the following formula (2)N 0 ：
（2）
In the method, in the process of the invention,D 1 the diameter of the driving disc is m;D 2 the diameter of the first-stage transmission disc is m;D 3 the diameter of the secondary transmission disc is m;D 4 the diameter of the driven disc is given in m.
Description: the rotating speed of a servo motor for driving the nose landing gear wheel can be calculated through the diameters of a driving disc and a primary driving disc in the driving device and the diameters of a secondary driving disc and a driven disc in the belt pulley assembly, so that a course speed simulation test can be accurately carried out.
Further, all can dismantle the connection through multiunit connecting bolt between first driven plate and the nose landing gear wheel and between second driven plate and the main landing gear wheel, be equipped with a plurality of lightening holes on the landing gear wheel, every group connecting bolt includes taper bolt and friction nut, friction nut install in lightening the hole, taper bolt comprises taper portion and screw thread portion, taper portion cooperation is installed in friction nut, screw thread portion is connected with the first screw hole that is equipped with on the first driven plate movable second driven plate.
Description: the landing gear machine wheel is provided with a lightening hole for lightening the weight, the driven disc is connected with the landing gear machine wheel through a connecting bolt and the lightening hole, the friction nut is arranged in the lightening hole and is fixed in the landing gear machine wheel through the friction force of the inner wall of the lightening hole, the conical part of the conical bolt is contacted with the friction nut, the threaded end penetrates into the driven disc nut to fix, and the friction nut is used for increasing the friction force between the conical bolt and the driven disc nut so as to improve the fastening force of connection. The stability and the safety of the installation of the driven disc and the landing gear wheels are improved through the connecting bolts.
Further, the taper angle of the taper portion is smaller than 6 °.
Description: when the conical bolt is under tension P, the load applied by the conical bolt to the friction nut and vertical to the conical surface is N, the load applied by the conical bolt to the axial direction of the conical bolt is P/tan theta, the vertical load applied by the friction nut to the inner wall of the lightening hole is P/tan theta, and the friction force between the inner wall of the lightening hole and the friction nut is mu.P/tan theta. The static friction coefficient mu between metals is larger than 0.1, so that the use requirement can be met by ensuring that the friction force provided by the inner wall of the lightening hole is larger than the tensile force provided by the taper bolt, namely mu/tan theta is larger than or equal to 1, and the use requirement can be met by ensuring that the angle of the taper surface is smaller than 6 degrees.
Further, the primary transmission disc and the secondary transmission disc are all arranged on the transmission shaft through connecting keys.
Description: the primary transmission disc and the secondary transmission disc are fixedly connected to the transmission shaft through the connecting key, so that the primary transmission disc and the secondary transmission disc are convenient to mount and dismount, and timely adjustment is conveniently carried out on the primary transmission disc and the secondary transmission disc in the test process.
Further, the first driven disc and the nose landing gear wheel and the second driven disc and the main landing gear wheel are detachably connected through a plurality of groups of connecting components;
the connecting assembly comprises a first connecting assembly arranged on the landing gear wheel and a second connecting assembly respectively arranged on the first driven disc or the second driven disc, the first connecting assembly comprises an inner cylinder body, an outer cylinder body and a plurality of hooks, the top of the inner cylinder body is fixedly connected with the landing gear wheel, the outer cylinder body is sleeved outside the inner cylinder body and is in limiting sliding connection with the inner cylinder body, the upper ends of the hooks are all rotationally connected with the lower end of the inner cylinder body through circular rings, a guide cylinder is arranged in the inner cylinder body, a guide groove is arranged in the guide cylinder, the top surface of the guide cylinder is rotationally connected with a threaded rod, the upper end of the threaded rod penetrates through the top surface of the inner cylinder body and is in matched transmission with a second threaded hole formed in the inner cylinder body, and a torsion spring for restoring the hooks is arranged on each circular ring;
a chute is arranged on the inner wall of the inner cylinder body, a pressing block which is matched with the chute to carry out limit sliding is arranged on the side wall of the outer cylinder body, a first air bag is arranged in the chute, the upper end of the first air bag is connected with the pressing block, the lower end of the first air bag is connected with the bottom surface of the chute, an air pipe communicated with the first air bag is arranged on the inner cylinder body, and a second air bag is arranged between the inner cylinder body and the top surface of the guide cylinder;
the second coupling assembling includes bottom plate, joint board and roof, bottom plate and first driven plate or second driven plate fixed connection, the joint inboard passes through cylinder and bottom plate fixed connection, the roof pass through the spring with cylinder fixed connection, the roof top surface be equipped with guide cylinder complex boss, the side of boss be equipped with guide way complex lug, be equipped with on the joint board with pothook one-to-one and be used for the opening that the pothook lower extreme stretches into, be located the roof bottom surface of opening top is equipped with the locking subassembly that is used for locking the pothook lower extreme, the joint board outside is equipped with the protecting crust that is used for protecting locking subassembly, protecting crust and roof sliding connection.
Still further, locking assembly includes first connecting rod, rotates and connects two second connecting rods of first connecting rod both sides and two one-to-one with the third connecting rod that the second connecting rod rotates and is connected, first connecting rod upper end and roof bottom surface fixed connection, the back shaft that is equipped with on third connecting rod middle part and the joint board rotates and is connected, all is equipped with the recess on the gib head both sides of pothook, slides on the joint board bottom surface and is equipped with be used for with recess cooperation joint's slider, and the third connecting rod lower extreme hinge have with the telescopic link that the slider is connected.
Description: the first driven plate and the front landing gear wheel and the second driven plate and the main landing gear wheel can be connected through the first connecting component and the second connecting component, parts such as the clamping hooks and the clamping plates are arranged, the first connecting component can be clamped on the second connecting component, the clamping plates are locked on the clamping plates through the locking components, the clamping hooks and the clamping plates are connected in a safer and more reliable mode, the connecting mode is simple to install and convenient to detach, the requirement that the first driven plate drives the front landing gear and the second driven plate drives the main landing gear wheel to rotate can be met, the difficulty in assembling the test belt rotating device with the landing gear wheel is reduced, the sliding grooves, the first air bags and the like are arranged, and the first connecting component and the second connecting component are more labor-saving and more convenient to assemble and disassemble through the action of the first air bags and the second air bags during installation and disassembly.
The invention provides a method for simulating the course speed of a double-wheel undercarriage in a full-machine drop test, which is based on the device for simulating the course speed of the double-wheel undercarriage in the full-machine drop test, and comprises the following steps:
s1, lifting an airplane to a preset height;
s2, controlling the landing gear wheel to rotate:
starting a servo motor of the first rotation device to drive the transmission assembly to operate, and driving the two groups of belt pulley assemblies to rotate simultaneously by the transmission assembly so as to enable the two nose landing gear wheels to rotate synchronously;
starting a servo motor of the second belt rotating device to drive the second driving disc to rotate, and driving the second driven disc to rotate through belt transmission by the second driving disc, so that the second driven disc drives the main landing gear wheel to rotate;
s3, after the rotating speeds of the current landing gear wheels and the main landing gear wheels reach preset rotating speeds, releasing the aircraft;
s4, the aircraft falls in free falling body movement, when the landing gear wheel is about to contact the ground, the light of the photoelectric switch is cut off, and the landing gear wheel is in a free rotation state and contacts the table top;
and S5, after the landing gear wheels contact the table top, starting measuring data.
The beneficial effects of the invention are as follows:
(1) According to the invention, one servo motor drives two wheels of the front landing gear to rotate through the belt rotating device at the same time, so that the driving equipment requirement can be reduced, the utilization rate of driving equipment is improved, and the type of follow-up belt rotating device is not used for a full-machine drop test at present;
(2) Because the nose landing gear of the carrier-based aircraft is usually of a double-wheel structure, the existing device adopts double motors to carry out belt rotation respectively, and the control precision and the additional mass of the belt rotation have great influence on a course speed simulation test;
(3) According to the invention, by arranging the photoelectric switch, the aircraft does free falling body movement and falls, and when the landing gear wheel is about to contact the ground, the automatic stop of the belt rotation is automatically triggered, so that the automatic stop of the belt rotation is realized;
(4) The mounting and connecting mode of the driven disc and the landing gear wheel has the advantages of simplicity and reliability in assembly and meets the requirements of a belt rotating device.
Drawings
FIG. 1 is a schematic illustration of the positional relationship of a landing gear wheel and a belt steering device of the present invention;
FIG. 2 is a schematic diagram of the position of the optoelectronic switch of the present invention;
FIG. 3 is a schematic perspective view of the steering gear of the present invention coupled to the nose landing gear wheels;
FIG. 4 is a schematic perspective view of a transmission assembly of the present invention;
FIG. 5 is a schematic diagram of the positional relationship between a first mount and a servo motor according to the present invention;
FIG. 6 is a schematic representation of the connection of the pulley assembly of the present invention;
FIG. 7 is a schematic perspective view of the steering gear of the present invention coupled to the main landing gear wheels;
FIG. 8 is a schematic diagram of the positional relationship between a second mount and a servo motor according to the present invention;
FIG. 9 is an exploded view of example 3 of the present invention;
FIG. 10 is a schematic illustration of the connection of a cone bolt and friction nut of the present invention;
FIG. 11 is a schematic diagram showing the relative positions of the first connecting component and the second connecting component according to the present invention;
FIG. 12 is a schematic view of the internal structure of the first connecting assembly of the present invention;
FIG. 13 is a schematic view of the internal structure of the second connection assembly of the present invention;
FIG. 14 is a schematic diagram showing the connection relationship between the first connecting component and the second connecting component according to the present invention;
FIG. 15 is a schematic view showing the connection relationship between the locking assembly and the hook according to the present invention;
wherein, 1-belt-turning assembly, 11-first belt-turning device, 111-servo motor, 112-first mount, 12-second belt-turning device, 121-second mount, 122-second driving disc, 123-second driven disc, 2-landing gear wheel, 21-nose landing gear wheel, 22-main landing gear wheel, 23-lightening hole, 24-connecting bolt, 241-cone bolt, 242-friction nut, 3-photoelectric switch, 4-transmission assembly, 41-transmission shaft, 42-first-stage transmission disc, 43-first driving disc, 5-pulley assembly, 51-second-stage transmission disc, 52-first driven disc, 6-first connecting assembly, 61-inner cylinder, 62-outer cylinder, 63-hook, 631-circular ring, 632-groove, 64-guide cylinder, 641-guide groove, 65-slide groove, 66-press block, 67-first air bag, 68-second air bag, 7-second connecting assembly, 71-bottom plate, 72-clip, 721-opening, 731-slide block, 73-732, 73-top plate, 732-spring-74-754, connecting rod, 7575-support cylinder, 7575-support rod assembly.
Detailed Description
The invention will be described in further detail with reference to the following embodiments to better embody the advantages of the invention.
Example 1: the device for simulating the course speed of the double-wheel landing gear in the full-aircraft drop test comprises a belt rotating assembly 1, a landing gear wheel 2 and two groups of photoelectric switches 3, wherein the belt rotating assembly 1 is arranged on an aircraft main body and is connected with the landing gear wheel 2; the two groups of photoelectric switches 3 are respectively arranged on the ground on the left side and the right side of the aircraft and are connected into a belt rotation control system; wherein, the belt-turning control system is in the prior art;
the landing gear wheels 2 include a nose landing gear wheel 21 and two sets of main landing gear wheels 22;
the belt-turning assembly 1 comprises a first belt-turning device 11 connected with the nose landing gear wheel 21 and two second belt-turning devices 12 connected with the main landing gear wheels 22 in a one-to-one correspondence;
as shown in fig. 3, the first belt rotating device 11 comprises a first mounting seat 112, a transmission assembly 4 mounted on the first mounting seat 112, a servo motor 111 for providing power for the transmission assembly 4, and two groups of belt pulley assemblies 5 connected with the transmission assembly 4, wherein the two groups of belt pulley assemblies 5 are detachably connected with two sides of a nose landing gear wheel 21 in a one-to-one correspondence manner;
as shown in fig. 7 and 8, the second belt rotating device 12 includes a second mounting seat 121, a second driving disc 122 mounted on the second mounting seat 121, a servo motor 111 for powering the second driving disc 122, and a second driven disc 123 in belt transmission connection with the second driving disc 122 through a belt, wherein the second driven disc 123 is detachably connected with the main landing gear wheel 22;
as shown in fig. 4 and 5, the transmission assembly 4 includes a transmission shaft 41, a primary transmission disc 42 and a first driving disc 43, the transmission shaft 41 is rotatably connected with a support block provided at the bottom of the first mounting seat 112, the primary transmission disc 42 is fixedly sleeved on the transmission shaft 41, the first driving disc 43 is connected with an output shaft of the servo motor 111, and the first driving disc 43 is in belt transmission connection with the primary transmission disc 42 through a belt;
as shown in fig. 6, the pulley assembly 5 includes a secondary driving disc 51 and a first driven disc 52, the secondary driving disc 51 is in belt driving connection with the first driven disc 52 through a belt, the first driven disc 52 is detachably connected with the nose landing gear wheel 21, and the secondary driving discs 51 of the two pulley assemblies 5 are respectively arranged at two ends of the driving shaft 41;
as shown in fig. 9 and 10, the first driven disc 52 and the nose landing gear wheel 21 and the second driven disc 123 and the main landing gear wheel 22 are detachably connected through a plurality of groups of connecting bolts 24, a plurality of lightening holes 23 are formed in the landing gear wheel 2, each group of connecting bolts 24 comprises a taper bolt 241 and a friction nut 242, the friction nut 242 is installed in the lightening hole 23, the taper bolt 241 is composed of a taper part and a threaded part, the taper part is installed in the friction nut 242 in a matching manner, and the threaded part is connected with a first threaded hole formed in the first driven disc 52 or the second driven disc 123;
the servo motor 111 and the photoelectric switch 3 are commercially available servo motors, photoelectric switches or appearance adjustment devices for being installed on the device.
Wherein the rotational speed of the landing gear wheel 2 in example 1 is calculated using the following equation 1N：
（1）
In the method, in the process of the invention,Vthe horizontal speed of the aircraft landing is in m/s;Dis the diameter of the landing gear wheel 2 in m.
Horizontal speed of aircraft landingVAt 80m/s, the diameter of the nose landing gear wheel 21 (outer edge of the inflated tire) is 0.5m, and the rotational speed of the nose landing gear wheel 21N51r/s;
the diameter of the main landing gear wheel 22 (outer edge of the inflated tire) is 0.7m, and the rotational speed of the main landing gear wheel 22N36r/s;
the rotation speed of the servo motor 111 driving the nose landing gear wheel 21 is calculated using the following equation 2N 0 ：
（2）
In the method, in the process of the invention,D 1 the diameter of the first active disc 43 in m;D 2 the diameter of the primary drive disk 42, in m;D 3 the diameter of the secondary transmission disc 51 is given by m;D 4 a unit m, which is the diameter of the second driven plate 123;
wherein,D 1 =D 2 =D 3 =D 4 200mm, the rotation speed of the servomotor 111 driving the nose landing gear wheel 21N 0 3060r/min;
the rotation speed of the servo motor 111 driving the main landing gear wheel 22 isWhere D6 is the diameter of the second driven disc 123 and D5 is the diameter of the second driving disc 122, d5=d6=200m, the rotation speed of the servo motor 111 driving the main landing gear wheel 22N 0 Is 2160r/min.
Example 2: the embodiment describes a method for simulating and testing the course speed of a double-wheel landing gear in a full-machine drop test, and the device for simulating and testing the course speed of the double-wheel landing gear in the full-machine drop test based on the embodiment 1 comprises the following steps:
s1, lifting an airplane to a preset height;
s2, controlling the landing gear wheel 2 to rotate:
starting a servo motor 111 of the first rotation carrying device 11 to drive a transmission assembly 4 to operate, wherein the transmission assembly 4 drives two groups of belt pulley assemblies 5 to rotate simultaneously, so that two nose landing gear wheels 21 rotate synchronously;
starting the servo motor 111 of the second belt rotating device 12 to drive the second driving disc 122 to rotate, and driving the second driven disc 123 to rotate by the second driving disc 122 through belt transmission, so that the second driven disc 123 drives the main landing gear wheel 22 to rotate;
s3, after the rotating speeds of the current landing gear wheels 21 and the main landing gear wheels 22 reach preset rotating speeds, releasing the aircraft;
s4, the aircraft falls in free falling body movement, when the landing gear wheel 2 is about to contact the ground, the light of the photoelectric switch 3 is cut off, and the landing gear wheel 2 is in a free rotation state and contacts the table top;
and S5, after the landing gear wheel 2 contacts the table top, starting measuring data.
Example 3: this embodiment differs from embodiment 1 in that the first driven disc 52 and nose landing gear wheel 21 and the second driven disc 123 and main landing gear wheel 22 are detachably connected by four sets of connection assemblies;
as shown in fig. 11, the connection assembly comprises a first connection assembly 6 provided on the landing gear wheel 2 and a second connection assembly 7 provided on the first driven disc 52 or the second driven disc 123, respectively;
as shown in fig. 12, the first connecting assembly 6 includes an inner cylinder 61, an outer cylinder 62 and four hooks 63, the top of the inner cylinder 61 is fixedly connected with the landing gear wheel 2, the outer cylinder 62 is sleeved outside the inner cylinder 61 and is in limited sliding connection with the inner cylinder 61, the lower end of the inner cylinder 61 is rotationally connected with the upper end of the hooks 63 through a circular ring 631, a guide cylinder 64 is arranged in the inner cylinder 61, a guide groove 641 is arranged in the guide cylinder 64, the top surface of the guide cylinder 64 is rotationally connected with a threaded rod 756, the upper end of the threaded rod 756 penetrates through the top surface of the inner cylinder 61 and is in matched transmission with a second threaded hole arranged on the inner cylinder 61, and a torsion spring for restoring the hooks 63 is arranged on each circular ring 631;
a chute 65 is arranged on the inner wall of the inner cylinder 61, a pressing block 66 which is matched with the chute 65 for limiting sliding is arranged on the side wall of the outer cylinder 62, a first air bag 67 is arranged in the chute 65, the upper end of the first air bag 67 is connected with the pressing block 66, the lower end of the first air bag 67 is connected with the bottom surface of the chute 65, an air pipe communicated with the first air bag 67 is arranged on the inner cylinder 61, and a second air bag 68 is arranged between the inner cylinder 61 and the top surface of the guide cylinder 64;
as shown in fig. 13, the second connecting assembly 7 includes a bottom plate 71, a clamping plate 72, and a top plate 73, the bottom plate 71 is fixedly connected with the first driven plate 52 or the second driven plate 123, the inner side of the clamping plate 72 is fixedly connected with the bottom plate 71 through a cylinder 74, the top plate 73 is fixedly connected with the cylinder 74 through a spring 731, a boss 732 matched with the guide cylinder 64 is provided on the top surface of the top plate 73, a bump 733 matched with the guide groove 641 is provided on the side of the boss 732, openings 721 corresponding to the hooks 63 one by one are provided on the clamping plate 72 for extending in the lower ends of the hooks 63, a locking assembly 75 for locking the lower ends of the hooks 63 is provided on the bottom surface of the top plate 73 above the openings 721, and a protective shell 755 for protecting the locking assembly 75 is provided on the outer side of the clamping plate 72;
as shown in fig. 14 and 15, the locking assembly 75 includes a first link 751, two second links 752 rotatably connected to two sides of the first link 751, and two third links 753 rotatably connected to the second links 752 in a one-to-one correspondence manner, the upper end of the first link 751 is fixedly connected to the bottom surface of the top plate 73, the middle part of the third link 753 is rotatably connected to a support shaft 754 provided on the clamping plate 72, grooves 632 are provided on two sides of a hook head of the hook 63, a slider 722 for engaging with the grooves 632 is slidably provided on the bottom surface of the clamping plate 72, and a telescopic rod connected to the slider 722 is hinged to the lower end of the third link 753.
The use method of the connecting component is as follows:
when the connecting device is installed, the first connecting component 6 and the second connecting component 7 are in butt joint, the guide cylinder 64 is sleeved on the outer side of the boss 732, the guide groove 641 moves towards the top plate 73 along the projection 733, the first air bag 67 is gradually extruded, the second air bag 68 is expanded through the air pipe, when the guide cylinder 64 is in contact with the top plate 73, the outer cylinder 62 is forced to slide on the inner cylinder 61, the outer cylinder 62 is close to the bottom plate 71 when in sliding, the outer cylinder is gradually contacted with the outer side of the clamping hook 63 and continuously extruded, the clamping hook 63 swings around the ring 631, the hook head of the clamping hook 63 is clamped into the opening 721, then the threaded rod 756 is rotated clockwise to enable the guide groove 641 to move downwards along the axial direction of the inner cylinder 61, the top plate 73 is also moved downwards to extrude the spring 731, the top plate 73 is moved downwards to enable the first connecting rod 751 to approach the clamping plate 72, the first connecting rod 751 is driven to move downwards to rotate, the two third connecting rods 753 rotate around the supporting shaft 754, the lower ends of the two third connecting rods 753 are close to each other, the sliding blocks 722 hinged with the third connecting rods 753 are also slid towards the corresponding sliding blocks 722, and the corresponding sliding blocks 63 are finally inserted into the grooves 722 are locked;
when the connecting device is disassembled, the threaded rod 756 is rotated anticlockwise, the guide cylinder 64 does not press the top plate 73 any more through the rebound of the second air bag 68 and the spring 731, the top plate 73 is reset upwards, the locking component 75 is driven to reset, the locking component 75 does not lock the hook head of the clamping hook 63 any more, then the outer cylinder 62 is pushed upwards to reset forcefully, the clamping hook 63 is reset under the action of the torsion spring, and therefore the first connecting component 6 is removed from the second connecting component 7.
Example 4: this embodiment differs from embodiment 3 in that the first driven disc 52 and nose landing gear wheel 21 and the second driven disc 123 and main landing gear wheel 22 are detachably connected by six sets of connection assemblies.
Claims (4)
1. The double-wheel landing gear course speed simulation test device in the full-aircraft drop test is characterized by comprising a belt rotating assembly (1), a landing gear wheel (2) and two groups of photoelectric switches (3), wherein the belt rotating assembly (1) is arranged on an aircraft main body and is connected with the landing gear wheel (2); the two groups of photoelectric switches (3) are respectively arranged on the ground on the left side and the right side of the aircraft and are connected with a belt rotation control system;
the landing gear wheels (2) comprise a nose landing gear wheel (21) and two sets of main landing gear wheels (22);
the belt rotating assembly (1) comprises a first belt rotating device (11) connected with the front landing gear wheel (21) and two second belt rotating devices (12) connected with the main landing gear wheel (22) in a one-to-one correspondence manner;
the first belt rotating device (11) comprises a first mounting seat (112), a transmission assembly (4) mounted on the first mounting seat (112), a first servo motor for providing power for the transmission assembly (4), and two groups of belt pulley assemblies (5) connected with the transmission assembly (4), wherein the two groups of belt pulley assemblies (5) are detachably connected with two sides of a nose landing gear wheel (21) in one-to-one correspondence respectively;
the second belt rotating device (12) comprises a second mounting seat (121), a second driving disc (122) mounted on the second mounting seat (121), a second servo motor for providing power for the second driving disc (122), and a second driven disc (123) which is in belt transmission connection with the second driving disc (122) through a belt, wherein the second driven disc (123) is detachably connected with the main landing gear wheel (22);
the transmission assembly (4) comprises a transmission shaft (41), a first-stage transmission disc (42) and a first driving disc (43), wherein the transmission shaft (41) is rotationally connected with a supporting block arranged at the bottom of a first mounting seat (112), the first-stage transmission disc (42) is fixedly sleeved on the transmission shaft (41), the first driving disc (43) is connected with an output shaft of a first servo motor, the first driving disc (43) is in belt transmission connection with the first-stage transmission disc (42) through a belt,
the pulley assembly (5) comprises a secondary transmission disc (51) and a first driven disc (52), the secondary transmission disc (51) is in belt transmission connection with the first driven disc (52) through a belt, the first driven disc (52) is detachably connected with the nose landing gear wheel (21), and the secondary transmission discs (51) of the two groups of pulley assemblies (5) are respectively arranged at two ends of the transmission shaft (41);
the first driven disc (52) and the front landing gear wheel (21) and the second driven disc (123) and the main landing gear wheel (22) are detachably connected through a plurality of groups of connecting components;
the connecting assembly comprises a first connecting assembly (6) arranged on the landing gear wheel (2) and a second connecting assembly (7) respectively arranged on the first driven disc (52) or the second driven disc (123);
the first connecting assembly (6) comprises an inner cylinder body (61), an outer cylinder body (62) and a plurality of clamping hooks (63), wherein the top of the inner cylinder body (61) is fixedly connected with the landing gear wheel (2), the outer cylinder body (62) is sleeved outside the inner cylinder body (61) and is in limit sliding connection with the inner cylinder body (61), the upper ends of the clamping hooks (63) are all rotationally connected with the lower end of the inner cylinder body (61) through circular rings (631), guide cylinders (64) are arranged in the inner cylinder body (61), guide grooves (641) are arranged in the guide cylinders (64), the top surfaces of the guide cylinders (64) are rotationally connected with threaded rods (756), the upper ends of the threaded rods (756) penetrate through the top surfaces of the inner cylinder body (61) and are in matched transmission with second threaded holes formed in the inner cylinder body (61), and torsion springs for resetting the clamping hooks (63) are arranged on the circular rings (631) respectively.
A chute (65) is arranged on the inner wall of the inner cylinder body (61), a pressing block (66) which is matched with the chute (65) for limiting sliding is arranged on the side wall of the outer cylinder body (62), a first air bag (67) is arranged in the chute (65), the upper end of the first air bag (67) is connected with the pressing block (66), the lower end of the first air bag is connected with the bottom surface of the chute (65), an air pipe communicated with the first air bag (67) is arranged on the inner cylinder body (61), and a second air bag (68) is arranged between the inner cylinder body (61) and the top surface of the guide cylinder (64);
the second connecting assembly (7) comprises a bottom plate (71), a clamping plate (72) and a top plate (73), the bottom plate (71) is fixedly connected with the first driven plate (52) or the second driven plate (123), the inner side of the clamping plate (72) is fixedly connected with the bottom plate (71) through a cylinder (74), the top plate (73) is fixedly connected with the cylinder (74) through a spring (731), a boss (732) matched with the guide cylinder (64) is arranged on the top surface of the top plate (73), a projection (733) matched with the guide groove (641) is arranged on the side edge of the boss (732), an opening (721) which corresponds to the clamping hooks (63) one by one and is used for extending in the lower end of the clamping hooks (63) is formed in the clamping plate (72), a locking assembly (75) used for locking the lower end of the clamping hooks (63) is arranged on the bottom surface of the top plate (73), a protecting shell (755) used for protecting the locking assembly (75) is arranged on the outer side of the clamping plate (72), and the protecting shell (755) is in sliding connection with the top plate (73).
The locking assembly (75) comprises a first connecting rod (751), two second connecting rods (752) which are rotationally connected to two sides of the first connecting rod (751), and two third connecting rods (753) which are rotationally connected to the second connecting rods (752) in a one-to-one correspondence mode, the upper ends of the first connecting rods (751) are fixedly connected with the bottom surface of a top plate (73), supporting shafts (754) which are arranged on the middle portions of the third connecting rods (753) and clamping plates (72) are rotationally connected, grooves (632) are formed in the two sides of a hook head of a hook (63), sliding blocks (722) which are used for being matched and clamped with the grooves (632) are arranged on the bottom surface of the clamping plates (72), and telescopic rods which are connected with the sliding blocks (722) are hinged to the lower ends of the third connecting rods (753).
2. A dual wheel landing gear speed simulation test apparatus in a full-flight drop test according to claim 1, wherein the rotational speed of the landing gear wheel (2) is calculated using the following formula (1)N：
（1）
In the method, in the process of the invention,Vthe unit is m/s for the horizontal speed of the aircraft landing;Dis the diameter of the landing gear wheel (2) and has the unit of m.
3. A dual-wheel landing gear speed simulation test apparatus in a full-aircraft drop test according to claim 1, wherein the rotation speed of the first servo motor driving the nose landing gear wheel (21) is calculated by the following formula (2)N 0 ：
（2）
In the method, in the process of the invention,D 1 is the diameter of the first active disc (43) in m；D 2 Is the diameter of a first-stage transmission disc (42), and the unit is m;D 3 the diameter of the secondary transmission disc (51) is m;D 4 is the diameter of the first driven disk (52) in m.
4. The device for simulating the course speed of the double-wheel landing gear in the full-aircraft drop test according to claim 1, wherein the primary transmission disc (42) and the secondary transmission disc (51) are both arranged on the transmission shaft (41) through connecting keys.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311429100.1A CN117141744B (en) | 2023-10-31 | 2023-10-31 | Dual-wheel landing gear course speed simulation test device in full-aircraft drop test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311429100.1A CN117141744B (en) | 2023-10-31 | 2023-10-31 | Dual-wheel landing gear course speed simulation test device in full-aircraft drop test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117141744A CN117141744A (en) | 2023-12-01 |
| CN117141744B true CN117141744B (en) | 2024-01-30 |
Family
ID=88908539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311429100.1A Active CN117141744B (en) | 2023-10-31 | 2023-10-31 | Dual-wheel landing gear course speed simulation test device in full-aircraft drop test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117141744B (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0972821A (en) * | 1995-09-06 | 1997-03-18 | Kao Corp | Drop testing machine |
| JP2008216160A (en) * | 2007-03-07 | 2008-09-18 | Sumitomo Precision Prod Co Ltd | Landing device testing apparatus of flying body and quick release mechanism |
| JP2010181318A (en) * | 2009-02-06 | 2010-08-19 | Sumitomo Precision Prod Co Ltd | Aircraft leg drop tester |
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN102053002A (en) * | 2010-12-09 | 2011-05-11 | 南京航空航天大学 | Drop test bed with speed controllable rotation driving mechanism |
| CN202149841U (en) * | 2011-07-08 | 2012-02-22 | 中国飞机强度研究所 | Follow-up device for driving airplane wheel in drop test of undercarriage |
| CN203287177U (en) * | 2013-05-30 | 2013-11-13 | 江西洪都航空工业集团有限责任公司 | An airplane wheel rotation-driving device |
| DE102013216920A1 (en) * | 2013-08-26 | 2015-02-26 | Airbus Operations Gmbh | Drop test device and method for performing a drop test |
| CN208828133U (en) * | 2018-08-17 | 2019-05-07 | 中航飞机起落架有限责任公司 | A kind of servo-actuated rotating equipment of multi-wheel and multi-support Aircraft Landing Gear Drop Test |
| CN208828090U (en) * | 2018-08-17 | 2019-05-07 | 中航飞机起落架有限责任公司 | A kind of undercarriage machine wheel rotating device of full electric servo control |
| CN217416148U (en) * | 2022-05-16 | 2022-09-13 | 沈阳市中飞机械厂有限公司 | Frequency conversion driving belt rotation detection device capable of being used by single or double wheels of undercarriage |
| CN115806057A (en) * | 2022-11-27 | 2023-03-17 | 中国飞行试验研究院 | Drop test bed and dynamic calibration method for undercarriage load measurement in load test flight |
| CN116902222A (en) * | 2023-09-15 | 2023-10-20 | 中国飞机强度研究所 | Belt rotating device and method suitable for single-wheel double-fork landing gear drop test of airplane |
-
2023
- 2023-10-31 CN CN202311429100.1A patent/CN117141744B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0972821A (en) * | 1995-09-06 | 1997-03-18 | Kao Corp | Drop testing machine |
| JP2008216160A (en) * | 2007-03-07 | 2008-09-18 | Sumitomo Precision Prod Co Ltd | Landing device testing apparatus of flying body and quick release mechanism |
| JP2010181318A (en) * | 2009-02-06 | 2010-08-19 | Sumitomo Precision Prod Co Ltd | Aircraft leg drop tester |
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test equipment and method of air vehicle landing gear |
| CN102053002A (en) * | 2010-12-09 | 2011-05-11 | 南京航空航天大学 | Drop test bed with speed controllable rotation driving mechanism |
| CN202149841U (en) * | 2011-07-08 | 2012-02-22 | 中国飞机强度研究所 | Follow-up device for driving airplane wheel in drop test of undercarriage |
| CN203287177U (en) * | 2013-05-30 | 2013-11-13 | 江西洪都航空工业集团有限责任公司 | An airplane wheel rotation-driving device |
| DE102013216920A1 (en) * | 2013-08-26 | 2015-02-26 | Airbus Operations Gmbh | Drop test device and method for performing a drop test |
| CN208828133U (en) * | 2018-08-17 | 2019-05-07 | 中航飞机起落架有限责任公司 | A kind of servo-actuated rotating equipment of multi-wheel and multi-support Aircraft Landing Gear Drop Test |
| CN208828090U (en) * | 2018-08-17 | 2019-05-07 | 中航飞机起落架有限责任公司 | A kind of undercarriage machine wheel rotating device of full electric servo control |
| CN217416148U (en) * | 2022-05-16 | 2022-09-13 | 沈阳市中飞机械厂有限公司 | Frequency conversion driving belt rotation detection device capable of being used by single or double wheels of undercarriage |
| CN115806057A (en) * | 2022-11-27 | 2023-03-17 | 中国飞行试验研究院 | Drop test bed and dynamic calibration method for undercarriage load measurement in load test flight |
| CN116902222A (en) * | 2023-09-15 | 2023-10-20 | 中国飞机强度研究所 | Belt rotating device and method suitable for single-wheel double-fork landing gear drop test of airplane |
Non-Patent Citations (1)
| Title |
|---|
| 舰载机全机落震试验方法;豆清波等;航空学报;第38卷(第03期);第175-183页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117141744A (en) | 2023-12-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112598960B (en) | Multi-degree-of-freedom motion platform for flight simulator and operation method | |
| CN106741854B (en) | A kind of rigidity decoupling empennage regulating mechanism | |
| CN109080729B (en) | Obstacle-surmounting mobile robot in pit | |
| CN112595540B (en) | Plant sampling system based on unmanned aerial vehicle platform and sampling method thereof | |
| CN104438922A (en) | Punching machine intelligent feeding-cropping mechanical arm | |
| CN107830358B (en) | Control device for electric adjusting bracket of accelerator | |
| CN117141744B (en) | Dual-wheel landing gear course speed simulation test device in full-aircraft drop test | |
| CN109050925A (en) | A kind of good buffer effect has the plant protection drone for being conveniently detached function | |
| CN108673128B (en) | Assembly devices of apparatus for producing of shaft coupling | |
| CN213458544U (en) | Multi-degree-of-freedom motion platform for flight simulator | |
| CN217155813U (en) | Wheel system load test equipment | |
| CN108045353B (en) | Supporting device for assembling and disassembling non-through disconnected axle | |
| CN111298367A (en) | Anti vertigo ability trainer of pilot | |
| CN204262223U (en) | Punch press intelligence loading and unloading manipulator | |
| US7559280B2 (en) | Adjustable link system | |
| CN210310925U (en) | Lifting adjustment platform in intelligent electric missile hanging vehicle | |
| CN212146292U (en) | Novel working platform | |
| CN110171575B (en) | Unmanned aerial vehicle with diversified protect function | |
| CN220357700U (en) | Multi-degree-of-freedom motion platform for aerospace flight simulator | |
| CN117068388B (en) | Free flight hooking simulation test system and method for airplane based on crushing device | |
| CN113478447B (en) | Electromechanical device troubleshooting device | |
| CN221438415U (en) | Anticollision formula unmanned aerial vehicle | |
| CN113335543B (en) | On-line monitoring power station equipment based on unmanned aerial vehicle in flight | |
| CN220618278U (en) | Auxiliary equipment for installing electromechanical equipment | |
| CN219533923U (en) | Ejection simulation training system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |